Now showing items 1-6 of 6
SCCREAM v.5: A Web-Based Airbreathing Propulsion Analysis Tool
(Georgia Institute of Technology, 1999-06)
To properly assess the advantages and disadvantages of various RBCC design options at the conceptual vehicle level, an engine performance analysis tool is required. This tool must be capable of modeling engine performance ...
SCCREAM (Simulated Combined-Cycle Rocket Engine Analysis Module): A Conceptual RBCC Engine Design Tool
(Georgia Institute of Technology, 1997-07)
Rocket-based combined-cycle engines are currently under consideration for use on future, reusable launch vehicles. By combining traditional rocket and airbreathing operating modes into a single engine, multi-mode RBCC ...
Integration of Cost and Business Simulation into Conceptual Launch Vehicle Design
(Georgia Institute of Technology, 1997-09)
This paper reports on research that integrates cost modeling and business simulation into conceptual design environments for advanced launch vehicle programs. A new design-oriented computer tool has been developed and used ...
Probabilistic Cost, Risk, and Throughput Analysis of Lunar Transportation Architectures
(Georgia Institute of Technology, 2006-03)
The President's Vision for Space Exploration presents a need to determine the best architecture and set of vehicle elements in order to achieve a sustained human lunar exploration program. The Lunar Architecture Stochastic ...
LASSO - Lunar Architecture Stochastic Simulator and Optimizer
(Georgia Institute of Technology, 2005-08)
The Lunar Architecture Stochastic Simulator and Optimizer (LASSO) is a simulation-based capability, based upon discrete event simulation (DES), for evaluating and optimizing flight element options for lunar transportation ...
Development of a Multipurpose Low Thrust Interplanetary Trajectory Calculation Code
(Georgia Institute of Technology, 2003-08)
A multipurpose low thrust interplanetary trajectory calculation code has been developed. This code integrates the equations of motion along the trajectory assuming that the spacecraft is subject to a single attracting body ...